Rocket vehicle with auxiliary staging structure and common fuel supply



May l1, 1965 o. R. sElDNER 3,182,593

ROCKET VEHICLE WITH AUXILIARY STAGING STRUCTURE AND COMMON FUEL SUPPLYOriginal Filed June 13, 1955 v H94. 265 /ss 262- 252 l .254 224 4' -zss3|6\ rall '256 26 29a Nl l :g2 266 -Qo l.; 2i?- 250127 a2 3o aso 'h2-:rszee ss SWITCH l INVENTOR. l

United States Patent O 3,182,593 RCCKET VEHICLE WITH AUXILIARY STAGINGSTRUCTURE ANI) COMMON FUEL SUPPLY Orville R. Seidner, Alhambra, Calif.,assigner to The Garrett Corporation, Los Angeles, Calif., a corporationof California Original application .lune 13, 1955, Ser. No. 515,183, nowPatent No. 2,962,934. Divided and this applition Dec. 1, 1960, Ser. No.73,022

8 Claims. (Cl. 102-49) This invention relates to vehicle propulsion ingeneral, and particularly relates to propulsion apparatus adaptable tovehicles of the rocket type.

This application is a division of application Serial No. 515,183, tiledlune 13, 1955 for: Vehicle Propulsion Apparatus, now Patent No.2,962,934.

Rocket propulsion is divided into three broad phases: (l) getting therocket off the ground and on its way, (2) accelerating the rocketthrough the dense atmosphere in the lower altitudes, and (3) propellingthe rocket thereafter. Since the rocket customarily must carry its ownfuel for all three phases, it is readily seen that the success lof thethird phase is governed almost solely by the economics effected in therst and second phases.

In the prior art it has been customary to provide liquid fuel andoxidant tanks within the rocket vehicle to supply the fuel nozzles inthe motor thereof. Since a considerable portion of the fuel is consumedin the first and second phases above-mentioned, it is readily seen thatany economies that can be effected in those phases will have beneficialeffects on the range or payload of the rocket because the fuel thussaved is then available for the third and most important phase.

In order to effect such economies it has been proposed to add a boosteror plurality of booster (commonly known as rocket steps or boosterstages) to the p-ayload rocket to lift the payload and accelerate itthrough .the dense air in the lower reaches of the atmosphere. Forexample, it is stated in Rockets, Missiles, and Space Travel, by WillyLey, published by The Viking Press, in 1952, that the WAC-Corporal insolo iiight (with a booster) attained an altitude of about 43.5 milesand the V-2 rocket attained a solo altitude of 114 miles, but when theWAC- Corporal was staged by the V-2 it reached 250 miles altitude. Ofparticular note is the fact that the V-2 required about 41/2 tons (dryweight) plus about 10 tons of fuel to stage the WAC-Corporal. Of the dryweight mentioned the rocket motor weighed one ton approximately.

Obviously, the dry weight of the -booster step constitutes a penaltysince it represents, in effect, a deadhead passenger taken along for theride.

I have discovered means for decreasing the dry weight of the booster orauxiliary step of a rocket vehicle. I have also discovered means forproviding starting assist to a single step rocket. Both discoveries arebased upon the principle that a rocket motor is ignorant of and notparticular about the source of the fuel fed to it, and that auxiliarymeans may be provided for furnishing external fuel either to the rocketmotor nozzle or to nozzle means apart from the included motor nozzle tofurnish thrust to the motor, hence to the rocket vehicle.

Therefore, the present invention is concerned with the rst and secondphases of rocket propulsion. Primarily, the invention has for its objectthe provision of methods and means for providing an auxiliary boost inthe launching of a rocket whereby the fuel usually expended in gettingthe rocket olf the ground is conserved for use in the later phases.Another object is to provide auxiliary assist propulsion apparatus whichwill allow conservation of the fuel in a rocket during the first andsecond phases of its flight. Other more specific objects will beapparent at once upon a consideration of the drawings when examined inthe light of the description which follows.

FIG. 1 is a cross-sectional view of one form of rocket motor, showing amethod of protecting the combustion chamber and throat of the motor;

FIG. 2 is an enlarged cross-section fragmentary view of a fuel-linecoupling which may be employed with the rocket of FIG. 3;

FiG. 3 is an elevation view, partlyv in cross-section, of an embodimentof the invention as applied to a free flight rocket; and

FIG. 4 is an velevation view, partly in cross-section, of an alternateembodiment of the invention as applied to a free flight rocket.

In rocket motors an intense heat is generated in the combustion chamberby the burning fuel. It has been suggested that the combustion chamber,the throat, and the motor exhaust nozzle could be protected to someextent by providing a jacket around them to provide an intermediatespace through which the fuel or oxidant could be conducted, in heatexchange, upstream from the fuel or oxidant nozzles. Patent No.2,695,496 shows such a structure.

In the practice of the present invention, as depicted by FIGS. 3 and 4,it is evident that no protective heat transfer will take place.Therefore, it is proposed, as shown in FIG, 1, to provide an expendableliner 92 within the exhaust nozzle 94 and the combustion chamber 96 ofthe motor 98. The liner 92 comprises a wall portion 93 shaped generallyin the form of a frustum to conform to the configuration of the exhaustnozzle 94 of the motor 98. The annular flanged portion 95, extendingradially from the larger open end of the frustum portion 93, is adaptedto engage and form a seal withtthe inner wall of the exhaust nozzle 94adjacent the lower end of the motor 9?. The upper end of the wall 93 issubstantially closed by a capped cylindrical portion 97 which extendsupwardly from the smaller end of the frustum, the capped end beingprovided with an orifice 99 for equalization of pressures on each sideof the liner 92. A shown, the cylindrical portion extends well into thecombustion chamber 96 of the motor 98. The liner may be fabricated oflead, for example, or any other material which is readily disintegratedby the heat in the motor 98 when it is being tired.

The space 100 between the liner 92 and the inner walls of the motor 98constitutes a jacketed chamber which may be nearly filled, for example,with water which will be converted to steam upon ignition of the fueland oxidant issuing from the fuel nozzle 162. As `the heat builds up inthe combustion chamber the liner 92 melts or crumbles, according to thenature of the expendable material from which it is fabricated, with aportion of the heat being utilized to convert the water to steam and tomelt the liner. In that manner the combustion chamber and throat areprotected during the initial buildup of thrust from the combustion ofthe fuel.

In FIG. 2 there is shown an enlarged cross-section fragmentary View of afuel-line coupling, such as disclosed in Patent No. 2,533,640, which maybe utilized with the propulsion apparatus as shown in FIG. 3. The

coupling member 116 comprises a male nipple 138 secured to the hull ofthe rocket and disposed at an acute angle to the vertical axis thereof.The member 134 comprises a mating female body 140 adapted to have asliding fit with the nipple 138 and to be secured thereto with thegasket seal 142 interposed, as shown. The securing means is adequatelyshown and described in the aforesaid Patent No. 2,533,640 and need notbe repeated herein. The securing means includes a locking and unlockinglever 144 arranged to be locked manually in the position shown and to beunlocked, for quick disconnect, by a pull on the cord 146. The distalend of the cord may be connected to the structure 166 shown in FIG. 3with the parts so arranged that a predetermined pull, occasioned by theinertia of structure 166 at the completion of one phase of flight by therocket vehicle, will cause the handle 144 to be drawn downwardly,thereby effecting disconnect between the members 116 and 134.

It will be appreciated that disconnect provision must be `made for bothfuel and oxidant, since these two liquids are obviously not carriedwithin a single conduit. Therefore, it is contemplatedthat the couplingdevice 136 will, in reality, comprise a pair of adjacent couplers, eachincluding a male nipple and female body, and each being releasable byconcurrent unlocking actuation.

A feature of the coupling is the ball check 148 which prevents fuel frombeing pumped back through the pipe 118, for example, and the ball check150 which closes off the external supply when the disconnect isaccomplished.

FIGS. 3 and 4 show embodiments of the invention applied to auxiliarystaging structures adapted to accompany the rocket vehicle during thefirst two phases of its flight. It is a feature of these embodimentsthat propulsion of the rocket is accomplished primarily by thrustgenerated in its own motor. The embodiment of FIG. 3 includes rocketmotors in the auxiliary staging structure for the preferred purpose ofmerely causing the structure to accompany the rocket until the externalfuel tanks are exhausted. With that type of construction, the auxiliarymotors need not be as large and heavy as would be the case if they wereto contribute any substantial thrust to the rocket. In the embodiment ofFIG. 4 the main rocket motor is utilized for all thrust purposes,including that of lifting the auxiliary staging booster and causing itto accompany the rocket until the external tanks are empty.

Referring now to FIG. 3, there is shown the lower motor section 150 of arocket adapted to have the fuel and oxidant nozzles 152 and 154 of itsmotor 156 fed by pumps 158 and 160 through the pipes 162 and 164 fromthe tanks in the rocket (not shown). An auxiliary staging structure 166comprises an annular shell 168 enclosing a pair of annular tanks 170 and172 which are adapted to constitute the external source of fuel andoxidant. Preferably, the tanks are paired as shown and extend completelyaround and within the nose of the shell 168. Such an arrangementprovides proper correlation (with respect to the axis of the rocket)between the probably different quantities of fuel and oxidant carriedand between their differing rates of consumption in flight.

Tank 170 has a connection by means of the pipe 174 with the nozzle 176in the rocket motor 178, and a connection by means of the pipe 180 withthe nozzle 182 in the rocket motor 184. Similarly, the tank 172 has aconnection by means of the pipe 186 with the nozzle 188 in the motor184, and a connection by way of the pipe 190 with the nozzle 192 in themotor 178. Pumps 194 and 196 are arranged to feed the fuel and oxidantfrom the tanks 170 and 172 to the p-ipes 174, 180 and pipes 186, 190.

Extending inwardly from the shell 168 are a pair of arms or struts 198and 200 provided at their inner ends with an annulus 202 arranged toabut the end surface 204 of the rocket section 150. Arm 198 is providedwith a passageway 206 which communicates at one end with the pump 194and at the other end with a coupling element 208. The passageway 206 hasa lateral branch 210 to the end of which is secured the pipe 212 whichfeeds a fluid nozzle 214 extending within the exhaust nozzle of themotor 156.

Arm 208 is provided with a passageway 216 which communicates at one endwith the pump 196 and at the other end with a coupling element 218. Thepassageway 216 has a lateral branch 220 to the end of which is securedthe pipe 222 which feeds a uid nozzle 224 extending within the exhaustnozzle of the motor 156.

Arranged within the rocket are the pipes 226 and 228 providingcommunication between the rocket motor fuel and oxidant nozzles 152, 154and the coupling elements 218, 288 by way of the mating couplingelements 230, 232 which are secured in the base of the motor sectionadjacent the end surface 204.

The paired coupling elements 218, 230 and 208, 232 may be of similarconstruction to those shown at 138, 140 in FIG. 2, or of any otherpreferred type.

Shutoff or check valves of suitable type are contemplated for thevarious fluid lines to prevent undue pressure on the lightweight tanksin the rocket and to prevent fuel and oxidant from being pumpedoverboard when the rocket steps part. One innovation might be a pressuresensitive switch 234 arranged to activate the pumps 158, upon cessationof pressure in pipe 226 upon exhaustion of auxiliary tank 172. All otherdetails of pipes, valves, and plumbing are clearly with-in the skill of`the rocket artisan.

It is now seen that the external source of fuel and oxidant in the tanksand 172 is available at the nozzles 152, 154, 214, and 224 for thrust inthe main rocket motor 156, and at the nozzles 176, 192, 182, and 188 forthrust in the auxiliary motors 178 and 184. It will be understood, ofcourse, that while there is shown a pair of auxiliary motors 17 8 and184, any number may be employed.

In FIG. 4 there is depicted a structure similar in many respects to thatof FIG. 3. The lower motor section 250 of the rocket is adapted to havethe fuel and oxidant nozzles 252 and 254 of its motor 256 fed by thepumps 258 and 260 through the pipes 262 and 264 from the tanks in therocket (not shown). An auxiliary staging structure 266 comprises anannular shell 268 enclosing a pair of tanks 270 and 272. In theconstruction shown the tanks would be semiannular, i.e., each wouldextend approximately half way around within the shell 268. Theconstruction is not critical, and the tanks could be annular, ifdesired, after the manner shown in FIG. 3.

Extending inwardly from the shell 268 (and disposed intermediate therocket fins) are a pair of arms or struts 274 and 276 joined at theirinner ends by a ring or annulus 278 arranged to abut the end surface 280of the rocket section 250. Arm 274 is provided with a passageway 282which communicates at one end with the pump 284 and at the other endwith a coupling element 286. Arm 276 is provided with a passageway 288which communicates at one end with the pump 290 and at the other endwith a coupling element 292.

Arranged within the rocket are the pipes 294 and 296 providingcommunication between the rocket motor fuel and oxidant nozzles 252, 254and the coupling elements 286, 292 by way of the mating couplingelements 298, 300 which are secured in the base of the motor section 250adjacent the end surface 280. The paired coupling elements 286, 298 and292, 300 are similar to those described above in connection with FIG. 3and need not be further detailed here.

The staging structure 266 is arranged to accompany the rocket. To thisend a plurality of releasable latches, one being shown at. 302, arearranged around the base of the motor section and the annulus 278intermediate the struts 274 and 276. For Ithe purpose of illustrationonly, the latch 302 is shown in a cut-away sectional view in FIG. 4 ascomprising a pair of dogs 304 and 306 pivotally secured to the motorsection 250 by means of the pins 308 and 310, respectively. The latchingends of the dogs are .arranged to engage the outwardly extendingshoulders of the annulus portion 312 which extends upwardly from theannulus 278. Unlatching action of the dogs is accomplished by thesolenoid 314 which, when energized, causes the dog members to pivotabout they pins 303 an-d 310 whereupon the latching ends of the dogs aredisengaged from the outwardly extending shoulders of the annulus portion312.

Means for energizing the solenoid 314 to accomplish the aforementionedunlatching action may include a pressure sensitive switch 316 subject tothe pressure in the auxiliary fluid feed pipe 294. Thus, when the uid inthe tank 270 is exhausted, the lowered pressure in the conduit 294actuates the switch 316 to close an electrical circuit, as shownschematically in FIG. 4, and thereby energize Ithe solenoid 314. Theelectrical circuit forms no part of the present invention since it couldbe easily devised by a skilled technician.

It will be appreciated, of course, that the latch details may be changedaccording to any preferred design, and that the form shown is merely forthe purpose of illustration, as aforementioned. Furthermore, the latchstructure shown in FIG. 4 may be incorporated in the embodiment shown inFIG. 3 and operated by the pressure sensitive switch 234.

In the practice of the invention as shown in FIGS. 3 and 4, the rocketis iired in the usual manner but with fuel and oxidant being suppliedfrom the external tanks in the auxiliary staging structures. When thefluid is exhausted in the external tanks, the pressure switches in theauxiliary feed lines are actuated to close their respective circuits. Inboth cases, the pressure switches may be arranged `to energize the mainfuel pumps in the rocket. Additionally, the pressure sensitive switch234 in FIG. 3 energizes the solenoid of the latch structure and thepressure switch 316 in the embodiment shown in FIG. 4 energizes thesolenoid 314 to unlatch the auxiliary staging booster from the rocket.If desired, fuel and oxidant may be supplied to all the rocket motors'from tanks (not shown) within the rocket vehicle.

It will now be seen that the invention comprises, in its broadestgeneral aspects, means for providing sources of liquid fuel and oxidantfor the propulsion of a vehicle. Additionally, novel means forintroducing the fuel and oxidant to the thrust region of a rocket motorhave been disclosed without any intent to limit the invention to themere details which have been described.

What is claimed is:

l. Propulsion apparatus for a rocket vehicle comprising: a primarythrust producing rocket motor; an auxiliary staging structure; aplurality of auxiliary thrust producing rocket motors mounted withinsaid auxiliary staging structure; means coupling said auxiliary stagingstructure to said rocket vehicle; means for uncoupling said auxiliarystaging structure from said rocket vehicle at the completion of onephase of flight by said rocket vehicle; means within said rocket vehiclefor supplying fuel and oxidant to said primary rocket motor; and commonmeans within said auxiliary staging structure for supplying fuel andoxidant selectively to said primary and auxiliary rocket motors.

2. Propulsion apparatus for a rocket vehicle comprising: a primarythrust producing rocket motor, an auxiliary staging structure; aplurality of auxiliary thrust producing rocket motors mounted withinsaid auxiliary staging structure; means coupling said auxiliary stagingstructure to said rocket vehicle; means for uncoupling said auxiliarystaging structure from said rocket vehicle at the completion of onephase of ight by said rocket vehicle; means Within hicle; means withinsaid rocket. vehicle for supplying fuel and oxidant to said primary andauxiliary rocket motors; and common means within said auxiliary stagingstructure for supplying fuel and oxidant to said rocket motors.

3. Propulsion apparatus for a rocket vehicle comprising: a primarythrust producing rocket motor; an auxiliary staging structure; aplurality of auxiliary thrust producing rocket motors mounted withinsaid auxiliary staging structure; means coupling said auxiliary stagingstructure to said rocket vehicle; means for uncoupling said auxiliarystaging structure from said rocket vehicle at the completion of onephase of flight by said rocket vesaid rocket vehicle for supplying fueland oxidant to said rocket motors; and means for supplying fuel andoxidant to said rocket motors from -a common source within saidauxiliary staging structure, said last mentioned means supplying fueland oxidant to said primary rocket motor and to said auxiliary rocketmotors for the first phase of flight by said rocket vehicle.

4. Propulsion apparatus for a rocket vehicle comprising: a primarythrust producing rocket motor, an auxiliary staging structure; aplurality of auxiliary thrust producing rocket motors mounted withinsaid auxiliary staging structure; means coupling said auxiliary stagingstructure to said rocket vehicle; means for uncoupling said auxiliarystaging structure from said rocket vehicle at rthe completion of onephase of flight by said rocket vehicle; a first means for supplying fueland oxidant to said primary rocket motor; a second means for supplyingfuel and oxidant -to said primary rocket motor, said second meanssupplying fuel and oxidant from a common source within said auxiliarystaging structure to said primary rocket motor and to said auxiliaryrocket motors prior to the uncoupling of said auxiliary stagingstructure from said rocket vehicle; fuel and oxidant to said primaryrocket motor from said second means to said first means upon exhaustionof fuel and oxidant in said second means.

5. Propulsion apparatus for a rocket vehicle in accordance with claim 4wherein said means for altering the supply of fuel and oxidant includespressure sensitive switch means responsive to fuel supply pressure, andmeans actuated by said pressure sensitive switch for supplying fuel andoxidant to said primary rocket motor from said first means of supply.

6. Propulsion apparatus for a rocket vehicle comprising: a primarythrust producing rocket motor; an auxiliary staging structure; aplurality of auxiliary thrust. producing rocket motors mounted withinsaid auxiliary staging structure; means coupling said auxiliary stagingstructure to said rocket Vehicle; means for effecting a separation ofsaid auxiliary staging structure from said rocket vehicle at thecompletion of one phase of flight by said rocket vehicle; means withinsaid rocket vehicle for supplying fuel and oxidant to said primaryrocket motor; and common means within said auxiliary staging structurefor supplying fuel and oxidant to said primary and auxiliary rocketmotors.

7. Propulsion apparatus for a rocket vehicle comprising: a primarythrust producing rocket motor; an auxiliary staging structure; aplurality of auxiliary thrust producing rocket motors mounted withinsaid auxiliary staging structure; means coupling said auxiliary stagingstructure to said rocket vehicle; means for uncoupling said auxiliarystaging struc-ture from said rocket vehicle at the completion of onephase of iiight by said rocket vehicle; and, means Within said rocketvehicle for supplying fuel and oxidant from a common source to saidprimary rocket motor and to said auxiliary rocket motors.

8. Propulsion apparatus for a rocket vehicle comprising; a primarythrust producing rocket motor; an auxiliary staging structure; meansWithin said auxiliary staging structure for supplying `fuel land oxidantto said primary rocket motor during one phase of flight by said rocketvehicle; means for coupling said auxiliary staging and means foraltering the supply of,

7 8 structure to said rocket vehicle; pressure sensitive switch2,686,473 8/ 54 Vogel 102,-49 means responsive to fuel pressure suppliedto said pri- 2,699,036 1/55 Nicholson 60--35.6 mary thrust producingrocket motor; and means actuated 2,726,510 12/55 Goddard 60-35.6 by saidpressure sensitive switch means for disconnecting 2,735,263 2/ 56Charshaan 60-35.6 said coupling means. 5 2,745,347 5/56 Lightbody et.al. 102-49 2,787,218 4/57 Anthony 102--49 References Cited by theExaminer UNITED STATES PATENTS BENJAMIN A. BORCHELT, Prl'nlafyExal'll'ler.

2,447,200 8/43 Miller 60 35'6 SAMUEL FEINBERG, ARTHUR M. HORTON,2,654,320 10/53 Schmid 1oz-49 10 Examiners-

1. PROPULSION APPARATUS FOR A ROCKET VEHICLE COMPRISING: A PRIMARYTHRUST PRODUCING ROCKET MOTOR; AN AUXILIARY STAGING STRUCTURE; APLURALITY OF AUXILIARY THRUST PRODUCING ROCKET MOTORS MOUNTED WITHINSAID AUXILIARY STAGING STRUCTURE; MEANS COUPLING SAID AUXILIARY STAGINGSTRUCTURE TO SAID ROCKET VEHICLE; MEANS FOR UNCOUPLING SAID AUXILIARYSTAGING STRUCTURE FROM SAID ROCKET VEHICLE AT THE COMPLETION OF ONEPHASE OF FLIGHT BY SAID ROCKET VEHICLE; MEANS WITHIN SAID ROCKET VEHICLEFOR SUPPLYING FUEL AND OXIDANT TO SAID PRIMARY ROCKET MOTOR; AND COMMONMEANS WITHIN SAID AUXILIARY STAGING STRUCTURE FOR SUPPLYING FUEL ANDOXIDANT SELECTIVELY TO SAID PRIMARY AND AUXILIARY ROCKET MOTORS.